CN115817872B - Variable pneumatic layout aircraft with gravity center adjusting function - Google Patents
Variable pneumatic layout aircraft with gravity center adjusting function Download PDFInfo
- Publication number
- CN115817872B CN115817872B CN202211623285.5A CN202211623285A CN115817872B CN 115817872 B CN115817872 B CN 115817872B CN 202211623285 A CN202211623285 A CN 202211623285A CN 115817872 B CN115817872 B CN 115817872B
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- wings
- tail
- gravity center
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000005484 gravity Effects 0.000 title claims abstract description 39
- 230000007246 mechanism Effects 0.000 claims abstract description 33
- 238000000034 method Methods 0.000 claims description 10
- 230000008569 process Effects 0.000 claims description 8
- 230000033001 locomotion Effects 0.000 claims description 7
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims description 5
- 238000013461 design Methods 0.000 description 8
- 238000010304 firing Methods 0.000 description 8
- 238000005265 energy consumption Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The invention discloses a variable pneumatic layout aircraft with a gravity center adjusting function, which comprises an aircraft body, wings, ailerons, tail wings, a propulsion propeller and a gravity center adjusting mechanism, wherein the aircraft body is provided with a plurality of air inlets; the wings are telescopic wings with variable expansion length and variable sweepback and are arranged on the left side and the right side of the middle part of the fuselage; the aileron is arranged at the trailing edge of the outer wing; the tail fin is an inverted V-shaped tail fin and can be folded on the side face of the middle rear section of the machine body; the propulsion propeller is arranged at the tail part of the machine body and can be folded and folded at a groove at the rear section in the machine body; the gravity center adjusting mechanism takes a battery as a balancing weight and is arranged in the machine body; the aircraft can reduce the resistance of flying in the air, has the capabilities of low-speed cruising and high-speed tracking, and ensures the flying stability.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a variable pneumatic layout aircrafts with a gravity center adjusting function.
Background
The variant unmanned aerial vehicle is a novel aircraft with the capability of detecting, monitoring and terminal damage. The working modes of the aircraft are divided into a launching tube folding storage mode, a high aspect ratio cruising mode, a low aspect ratio sweepback tracking mode and a terminal sweepback angle attack damage mode, and the working modes can be switched according to task requirements.
The unmanned aerial vehicle can be used for executing various tasks such as battlefield reconnaissance monitoring, positioning and shooting correction, damage evaluation, electronic war and the like, and compared with the traditional fixed-wing aerial vehicle, the variant aerial vehicle suitable for launching tube launching deployment has the advantages of small size, good portability, high damage precision and the like, can be quickly launched to the upper air of a war area to execute the tasks in a helicopter air shooting or ground launching vehicle launching mode, and is particularly suitable for amphibious landing war, urban environment war, multi-machine cooperative cluster and the like.
At present, the international variant aircraft mostly takes the configuration of a spring knife unmanned aerial vehicle as a reference, adopts a front and rear double-wing folding design scheme, has small wing aspect ratio in a cruising state and large tail wing area, causes various problems of large resistance, high energy consumption, short cruising time, small operational radius and the like in the flying process, cannot execute long-time and long-distance investigation and monitoring tasks, and has poor battlefield environment adaptability; in addition, the wings of the existing folding wing variant aircraft mostly adopt the design scheme of torsion springs for opening and locking positions, so that variant flight in a wide-speed domain is difficult to carry out, a ground or sea surface high-speed moving target cannot be tracked, meanwhile, when the tail end attacks the target, the flying speed is low, the maneuverability is poor, the wing is easy to intercept by air fire prevention, and the capability of executing tasks of the tubular launching aircraft is severely limited.
Disclosure of Invention
The invention aims to provide a variable pneumatic layout aircraft with a gravity center adjusting function, which solves the problems of high energy consumption, short cruising time, short range, small flying speed domain, poor battlefield environment adaptability and the like of the conventional tubular launching folding wing variant aircraft.
The technical solution for realizing the purpose of the invention is as follows:
A variable pneumatic layout aircraft with a gravity center adjusting function comprises a fuselage, wings, ailerons, tail wings, a propulsion propeller and a gravity center adjusting mechanism; the method is characterized in that:
the wings are telescopic wings with variable expansion length and variable sweepback and are arranged on the left side and the right side of the middle part of the fuselage;
the aileron is arranged at the trailing edge of the outer wing;
The tail fin is an inverted V-shaped tail fin and can be folded on the side face of the middle rear section of the machine body;
the propulsion propeller is arranged at the tail part of the machine body and can be folded and folded at a groove at the rear section in the machine body;
The gravity center adjusting mechanism is installed inside the machine body by taking a battery as a balancing weight.
Compared with the prior art, the invention has the remarkable advantages that:
(1) In the aspect of variable pneumatic layout design, a cylindrical pneumatic layout mode is adopted after folding, and the pneumatic layout mode can be rapidly put in a combat area to perform tasks in the sky through the modes of helicopter air firing, ground firing vehicle firing or naval vessel firing, so that the diversity of firing modes is realized, and meanwhile, the resistance of flying in the sky is greatly reduced.
(2) In the aspects of light weight and miniaturization design, materials with high strength and high mass ratio such as carbon fiber, glass fiber and the like are adopted to form an unconventional novel compression-resistant machine body, so that the aircraft can keep good balance between weight and strength. The telescopic wing adopts an inner side wing and outer side wing nested design, reduces the volume of the aircraft and the space required by the aircraft during take-off, reduces the weight of the aircraft, and accords with the development trend of light weight of the aircraft. In order to achieve miniaturization of the aircraft, the arrangement and deformation forms of wings, tail wings and propellers are optimized; wings shrink and sweep back by 90 degrees, and the wings on the left side and the right side can be overlapped and collected above the middle rear section of the fuselage; the tail fin is tightly attached to two sides of the machine body after being rotated and folded around the fixed shaft; two paddles of the propeller can be respectively accommodated in an upper groove and a lower groove of the middle rear section of the machine body; when the three are folded and unfolded at the same time, the unmanned aerial vehicle is cylindrical, and is favorable for storage, carrying and tubular emission of the unmanned aerial vehicle.
(3) In the aspect of multi-mode conversion, as the flight conditions of the aircraft in various flight modes are different, the preloaded torsion spring is adopted to enable the tail wing to be rapidly unfolded, so that the rapid conversion from the folded state to the flight state is realized; the high aspect ratio mode realizes long-time cruising by controlling the aspect ratio; the small aspect ratio changes the sweep-back mode and simultaneously controls the aspect ratio and the sweep-back angle, so that synchronous tracking is realized; in the scheme of the invention, the wing rotates under the action of the driving mechanism, and the magnitude of the wing sweepback angle is symmetrically changed, so that the aircraft has the capabilities of low-speed cruising and high-speed tracking.
(4) The invention designs a gravity center adjusting mechanism, when a conventional sweepback aircraft changes a wing from a small sweepback angle to a large sweepback angle position, the pneumatic center of the wing moves far back than the gravity center, and the longitudinal balance of the aircraft is seriously affected. The steering engine is fixed on the platform, and transmits power output to the screw rod through the coupler, and the screw rod nut is matched with the screw rod and fixedly connected with the base; the screw nut moves along the axial direction of the screw to drive the battery to translate along the axial direction of the machine body, and the battery moves back and forth to adjust the gravity center of the aircraft in the process that the wing changes to be sweepback, so that the longitudinal stability of the flight is ensured.
Drawings
Fig. 1 is a schematic structural view of a folding and storage mode of a transmitting tube according to the present invention.
Fig. 2 is a schematic view of the structure of the high aspect ratio cruise mode of the present invention.
FIG. 3 is a schematic diagram of the structure of the low aspect ratio sweep tracking mode of the present invention.
FIG. 4 is a schematic diagram of the structure of the present invention in a damage mode of a tip-large sweep attack.
Fig. 5 is a schematic view of the position of the center of gravity adjustment mechanism.
Fig. 6 is an assembled schematic view of the sweepback drive mechanism.
Fig. 7 is an assembly schematic of the center of gravity adjustment mechanism.
Fig. 8 is a schematic view of the installation of the lead screw and the lead screw nut.
Fig. 9 is a schematic view of the installation and movement of the battery.
Wherein: 1-fuselage, 2-inboard wing, 3-outboard wing, 4-aileron, 5-tail wing, 6-flexible fairing, 7-propeller, I-swept drive, II-center of gravity adjustment mechanism, 11-large steering engine, 12-elastic coupling, 13-worm, 14-worm gear, 21-steering engine, 22-coupling, 23-lead screw, 24-lead screw nut, 25-base, 26-battery, 27-slide rail, 28-platform, 29-bearing housing, 30-bearing
Detailed Description
The invention is further described with reference to the drawings and the detailed description.
As shown in fig. 1, the variable aerodynamic configuration aircraft with a center of gravity adjusting function of the present invention includes a fuselage 1, a pair of telescopic wings (an inner wing 2 and an outer wing 3) with variable extension and sweep, a pair of ailerons 4, an inverted V-shaped tail 5, a flexible fairing 6 and a propulsion propeller 7. The fuselage 1 adopts a cylindrical appearance layout after folding, a pair of telescopic wings with variable expansion length and variable sweep are arranged on two sides of the middle part of the fuselage 1, the inner side wing 2 is nested with the outer side wing 3, the aerodynamic performance of the aircraft is changed by adjusting the span and sweep angle of the deformable wings, and a pair of ailerons 4 are arranged at the rear edge of the outer side wing 3. The pair of tail fins 5 are of inverted V shape, are arranged at the middle and rear sections of the machine body 1 through torsion springs, are tightly attached to the machine body 1 after being folded, and the flexible cowling 6 on the left side and the right side of the machine body 1 is covered on a control mechanism of the tail fins for improving air flow performance, and the propulsion propeller 7 is arranged at the tail part of the machine body 1 and can be folded and unfolded at a groove of the middle and rear sections of the machine body 1. A set of gravity center adjusting mechanism II is additionally arranged in the fuselage 1, and when the sweepback changing mechanism I operates and the sweepback angle of the wing changes, the gravity center of the aircraft can be synchronously adjusted, so that the longitudinal stability of the flight is ensured.
Fig. 2-4 show three flight modes during flight, fig. 5 shows the relative positions of the two sets of drive mechanisms, fig. 6 shows a specific assembly and movement process of the sweepback drive mechanism i, and fig. 7-9 show a specific assembly and movement process of the center of gravity adjustment mechanism ii.
The sweepback driving mechanism comprises a large steering engine 11, an elastic coupling 12, a worm 13 and a worm wheel 14. The large steering engine 11 transmits power output to the worm 13 through the elastic coupling 12, the worm 13 is meshed with the worm wheel 14 for transmission, and the worm wheel 14 drives the telescopic wing to rotate through the rotating rod, so that the change of the sweepback angle of the telescopic wing is realized.
The gravity center adjusting mechanism comprises a steering engine 21, a coupling 22, a screw rod 23, a screw rod nut 24, a base 25, a battery 26, a sliding rail 27, a platform 28, a bearing seat 29 and a bearing 30. The battery 26 is fixed on the base 25 and is used as a power source and a balancing weight, so that the weight of the aircraft is greatly reduced; the steering engine 21 is fixed on the platform 28, and transmits power output to the screw rod 23 through the coupler 22; the screw nut 24 is matched with the screw 23 and fixedly connected with the base 25; the sliding blocks in the sliding rails 27 are fixed on the base 25, and the guide rails are fixed on the platform 28, so that the sliding blocks are matched with the guide rails on one hand, the battery can only move along the axial direction of the machine body, and on the other hand, the battery 26 can be supported; a pair of bearings 30 are mounted at both ends of the screw rod 23, the bearings 30 are mounted in a bearing housing 29, and the bearing housing 29 is fixed inside the machine body 1.
When the sweepback angle of the wing is changed, the power output of the large steering engine 11 is transmitted to the wing through the worm 13 and the worm wheel 14, the sweepback angle of the wing is changed, meanwhile, the other steering engine 21 starts to operate under the action of the flight control system, the power is transmitted to the base 25 through the screw nut groups 23 and 24, and the movement of the battery 26 is controlled to adjust the gravity center of the aircraft. To ensure the longitudinal stability of the flight, the movement distance of the center of gravity and the pressing center (pneumatic center) of the aircraft is basically equal, namely
Wherein a and b respectively represent equivalent lengths of the left (or right) side wing pressing center, the gravity center and the rotating shaft center along the expanding length direction, θ represents a sweepback angle, m 1 represents the mass of a battery (balancing weight), m 2 represents the wing weight, m represents the total mass of the aircraft, and Deltax represents the moving distance of the battery.
The mechanism realizes aircraft center of gravity adjustment through a screw nut structure, thereby matching aerodynamic center change caused by wing sweepback angle change.
The front half part of the machine body of the scheme is cylindrical, and can be rapidly put in the air of a combat area to perform tasks in a mode of helicopter air firing, ground launching vehicle firing or ship blasting under a folding state. The middle part of the aircraft body is provided with a pair of telescopic wings with variable expansion length and variable sweep, the inner side wing 2 is fixed relative to the aircraft body in a nested manner, the outer side wing 3 slides relative to the inner side wing 2 to adjust the wing span, so that the aspect ratio of the wings is increased, the induced resistance and the energy consumption are further reduced, and the cruising time of the aircraft is increased; meanwhile, a driving mechanism I is designed to control the sweepback angle of the wing, the wing is changed into the sweepback wing in the tail end attack stage, and the flying speed is increased, so that the burst prevention probability is improved. A pair of ailerons 4 are arranged at the rear edge of the outer wing 3, and the lateral stability of the aircraft can be increased by the rolling moment generated by the differential deflection of the left and right ailerons; the pair of inverted V-shaped tail wings 5 cling to the machine body before being launched, the tail wings can be quickly rotated and unfolded around the tail wing fixing shaft through devices such as torsion springs and the like after being launched, a crank-link mechanism is arranged in the machine body, and the swinging of the link rod transmits motion to the main beam of the tail wings through the middle rod, so that the tail wings are driven to deflect. When two quarter rudder surfaces deflect in the same direction, the aircraft plays a role of an elevator to control the pitching of the aircraft; when the two sides of the control surface deflect differentially, the control surface acts as a rudder to control the yaw of the aircraft. The flexible fairing 6 covers the control mechanism of the flight for improving the airflow characteristics. The propulsion propeller 7 is installed at the tail of the fuselage 1 and is used for providing thrust required during flight, and the propeller blades can be folded and retracted at the groove of the rear section in the fuselage 1 before launching.
The process of mission execution by a variant aircraft of this solution can generally be divided into three phases:
(1) The transmitting stage: the outer wings, the tail wings and the propulsion propellers are contracted and folded in the corresponding positions of the fuselage, so that the length of the launching tube is reduced, and the device is convenient to carry. The tail wing and the propeller automatically spring out after the firing, and meanwhile, the wing is rapidly unfolded to be in a straight configuration by virtue of the driving mechanism.
(2) Cruising phase: after the wings are unfolded, the outer wings are quickly stretched outwards through telescopic mechanisms (such as steering engines), the aspect ratio can be automatically adjusted according to the actual task environment requirements, so that the induced resistance and the energy consumption are reduced, and the cruising time is increased.
(3) End attack stage: after the object is found, the outer wing contracts inwards, and meanwhile, the wing is changed into a sweepback wing by virtue of a driving mechanism, so that the flying speed of the tail end is improved, and the maneuverability and flexibility in the sudden prevention process are improved. In the wing sweepback process, the aerodynamic center of the whole aircraft is far moved backwards than the gravity center, and the aircraft is easy to be unstable. At this time, the gravity center adjusting mechanism can automatically adjust the position of the battery to ensure the longitudinal stability of the aircraft.
The aircraft body structure is made of high-strength and high-mass ratio materials such as carbon fiber reinforced composite materials in a large range, and the weight is reduced on the premise of meeting the strength requirement; in the aspect of design of the variable configuration mechanism, the telescopic wings 2 and 3, the inverted V-shaped tail wing 5 and the propulsion propeller 6 can be folded and unfolded, so that the design requirement of miniaturization is met. In the aspect of multi-mode conversion, a set of control systems with different flight modes are designed, and the aspect ratio is controlled through the displacement of the outer side wing 3 relative to the inner side wing 2 in a high aspect ratio cruising mode, so that long-time cruising is realized; the small aspect ratio changes a sweep-back tracking mode, and simultaneously controls the aspect ratio and the sweep-back angle, so that synchronous tracking is realized; the damage mode of the end large sweepback attack controls the sweepback angle through the rotation angle of the wing, and the end attack speed is increased.
Claims (6)
1. A variable pneumatic layout aircraft with a gravity center adjusting function comprises a fuselage, wings, ailerons, tail wings, a propulsion propeller and a gravity center adjusting mechanism; the method is characterized in that:
the wings are telescopic wings with variable expansion length and variable sweepback and are arranged on the left side and the right side of the middle part of the fuselage;
the aileron is arranged at the trailing edge of the outer wing;
The tail fin is an inverted V-shaped tail fin and can be folded on the side face of the middle rear section of the machine body;
the propulsion propeller is arranged at the tail part of the machine body and can be folded and folded at a groove at the rear section in the machine body;
The gravity center adjusting mechanism takes a battery as a balancing weight, is arranged in the fuselage and is used for adjusting the gravity center of the aircraft to match with the change of the aerodynamic center caused by the change of the sweepback angle of the wing;
The gravity center adjusting mechanism includes: steering engine, shaft coupling, lead screw nut, base, slide rail, platform, bearing frame and bearing;
The steering engine is fixed on the platform, and transmits power output to the screw rod through the coupler, and the screw rod nut is matched with the screw rod and fixedly connected with the base;
the sliding block in the sliding rail is fixed on the base, the guide rail is fixed on the platform, and the screw nut moves along the axial direction of the screw rod to drive the battery to translate along the sliding rail;
the battery is fixed on the base and is used as a power source and a balancing weight.
2. The variable aerodynamic configuration aircraft with center of gravity adjustment of claim 1, wherein: the gravity center adjusting mechanism satisfies the following conditions when adjusting:
Wherein a and b respectively represent equivalent lengths of the single-side wing press center, the gravity center and the rotating shaft center along the extending direction, θ represents a sweepback angle, m 1 represents a battery mass, m 2 represents a wing weight, m represents a total mass of the aircraft, and Δx represents a distance of battery movement.
3. The variable aerodynamic configuration aircraft with center of gravity adjustment of claim 1, wherein: the wing includes an inboard wing and an outboard wing.
4. The variable aerodynamic configuration aircraft with center of gravity adjustment of claim 1, wherein: the tail fin is arranged at the middle rear section of the machine body through a torsion spring.
5. The variable aerodynamic configuration aircraft with center of gravity adjustment of claim 1, wherein: the left and right sides of the upper body are provided with flexible fairings which are covered on the control mechanism of the tail wing.
6. The variable aerodynamic configuration aircraft of any one of claims 1-5, wherein: comprising three flight phases:
(1) The transmitting stage: the wings, the tail wings and the propulsion propellers are contracted, the tail wings and the propulsion propellers automatically spring open after being launched, and meanwhile, the wings are unfolded to be in a straight configuration;
(2) Cruising phase: after the wings are unfolded, the outer wings are stretched outwards;
(3) End attack stage: after the object is found, the outer wing contracts inwards and becomes a sweepback wing at the same time, and in the sweepback process of the wing, the gravity center adjusting mechanism ensures the longitudinal stability of the aircraft by automatically adjusting the position of the battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211623285.5A CN115817872B (en) | 2022-12-16 | 2022-12-16 | Variable pneumatic layout aircraft with gravity center adjusting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211623285.5A CN115817872B (en) | 2022-12-16 | 2022-12-16 | Variable pneumatic layout aircraft with gravity center adjusting function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115817872A CN115817872A (en) | 2023-03-21 |
| CN115817872B true CN115817872B (en) | 2024-05-24 |
Family
ID=85516271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211623285.5A Active CN115817872B (en) | 2022-12-16 | 2022-12-16 | Variable pneumatic layout aircraft with gravity center adjusting function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115817872B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117874928B (en) * | 2024-03-11 | 2024-05-14 | 中国民用航空飞行学院 | Lightweight design method for V-shaped tail wing of fixed wing unmanned aerial vehicle |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB713525A (en) * | 1951-02-12 | 1954-08-11 | Leslie Everett Baynes | Improvements in high speed aircraft |
| CN102267557A (en) * | 2011-04-27 | 2011-12-07 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN203601574U (en) * | 2013-12-04 | 2014-05-21 | 广州地理研究所 | Single-rotation-wing power-driven unmanned plane balance adjusting device |
| CN109436296A (en) * | 2018-12-26 | 2019-03-08 | 西北工业大学 | The folding wings unmanned plane and its launching technique of cartridge type transmitting |
| CN110844071A (en) * | 2019-12-04 | 2020-02-28 | 北京航空航天大学 | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight |
| CN111942577A (en) * | 2020-08-13 | 2020-11-17 | 北京京东乾石科技有限公司 | Gravity center balancing method of unmanned aerial vehicle and unmanned aerial vehicle |
| CN112520012A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Wing expanding length-variable sweepback-variable mechanism of unmanned aerial vehicle |
| CN114228976A (en) * | 2021-12-10 | 2022-03-25 | 南京理工大学 | Control mechanism suitable for folding and unfolding of aircraft wing |
-
2022
- 2022-12-16 CN CN202211623285.5A patent/CN115817872B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB713525A (en) * | 1951-02-12 | 1954-08-11 | Leslie Everett Baynes | Improvements in high speed aircraft |
| CN102267557A (en) * | 2011-04-27 | 2011-12-07 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN203601574U (en) * | 2013-12-04 | 2014-05-21 | 广州地理研究所 | Single-rotation-wing power-driven unmanned plane balance adjusting device |
| CN109436296A (en) * | 2018-12-26 | 2019-03-08 | 西北工业大学 | The folding wings unmanned plane and its launching technique of cartridge type transmitting |
| CN110844071A (en) * | 2019-12-04 | 2020-02-28 | 北京航空航天大学 | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight |
| CN111942577A (en) * | 2020-08-13 | 2020-11-17 | 北京京东乾石科技有限公司 | Gravity center balancing method of unmanned aerial vehicle and unmanned aerial vehicle |
| CN112520012A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Wing expanding length-variable sweepback-variable mechanism of unmanned aerial vehicle |
| CN114228976A (en) * | 2021-12-10 | 2022-03-25 | 南京理工大学 | Control mechanism suitable for folding and unfolding of aircraft wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115817872A (en) | 2023-03-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3560820B1 (en) | Aerial vehicle with deployable components | |
| CN107176286B (en) | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle | |
| CN107972869B (en) | Variable-configuration double-body cross-water-air-medium unmanned aerial vehicle | |
| CN109229376B (en) | Cross-domain amphibious carrier | |
| RU2563921C1 (en) | Rotorcraft with vertical takeoff | |
| EP3705401A1 (en) | Assembly of three composite wings for aerial, water, land or space vehicles | |
| CN110077588A (en) | It is a kind of can the sea, land and air latent four of VTOL dwell aircraft | |
| CN103204237B (en) | Aerial propelling device suitable for amphibious unmanned aerial vehicle | |
| EP3668786B1 (en) | Actuating system | |
| CN115817872B (en) | Variable pneumatic layout aircraft with gravity center adjusting function | |
| CN113148112A (en) | Telescopic wing mechanism suitable for small unmanned aerial vehicle | |
| US11873086B2 (en) | Variable-sweep wing aerial vehicle with VTOL capabilites | |
| CN114394233A (en) | Sea-air amphibious cross-medium bionic aircraft and working method thereof | |
| CN218786088U (en) | Water-air amphibious cross-medium aircraft | |
| CN111890858A (en) | Cross-medium aircraft | |
| US4296896A (en) | VTOL Airplane | |
| CN110844071A (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight | |
| CN212423467U (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight | |
| CN112520012A (en) | Wing expanding length-variable sweepback-variable mechanism of unmanned aerial vehicle | |
| CN115648870A (en) | Water-air amphibious cross-medium unmanned aerial vehicle | |
| KR20160064413A (en) | Unmanned Aerial Vehicle having joined wings and delta wings | |
| CN110775263B (en) | Tailstock type air-sea cross-region unmanned aerial vehicle | |
| CN209192220U (en) | Scissor DCB Specimen seesaw type autogyro | |
| CN218316113U (en) | Water-air amphibious cross-medium unmanned aerial vehicle | |
| US20240174353A1 (en) | Vertical take-off and landing aircraft based on variable rotor-wing technology and dual rotor-wing layout |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |